单组元肼推力器温度场仿真及试验

推进技术 ›› 2005, Vol. 26 ›› Issue (1): 1-4.

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单组元肼推力器温度场仿真及试验

王超,周旭东,汤建华,孙磊,华巍,杨建辉,杨玲琴

上海航天动力机械研究所上海200233;上海航天技术研究院;上海200233;上海航天动力机械研究所上海200233;上海航天动力机械研究所上海200233;上海航天动力机械研究所上海200233;上海航天动力机械研究所上海200233;上海航天动力机械研究所上海200233

发布日期:2021-08-15

Numerical and experimental studies for temperature field of monopropellant hydrazine thruster

Shanghai Spaceflight Inst. of Power Machinery, Shanghai 200233,China;Shanghai Spaceflight Inst. of Power Machinery, Shanghai 200233,China;Shanghai Spaceflight Inst. of Power Machinery, Shanghai 200233,China;Shanghai Spaceflight Inst. of Power Machinery, Shanghai 200233,China;Shanghai Spaceflight Inst. of Power Machinery, Shanghai 200233,China;Shanghai Spaceflight Inst. of Power Machinery, Shanghai 200233,China

Published:2021-08-15

摘要/Abstract

摘要： 针对 5N单组元肼推力器, 建立了在轨运行过程中推力室热控组件的传热模型; 应用有限元方法进行了热分析和仿真计算; 并对计算结果进行地面热真空试验验证。对于进一步开发、研制具有新型结构和热控性能的姿控推力器和具有相似结构的多种推力器具有一定的借鉴和指导意义。

关键词: 单元推进剂火箭发动机;热控制;温度场;热分析;仿真模型

Abstract: Heat transfer model on the thermal control groupware of thrust chamber for orbit 5N propellant hydrazine thruster is established. Thermal analysis and numerical computing with finite element method are fully performed. Then computed results are validated in heat vacuum test. As a result, significant references and useful guidance are supplied for further developing and manufacturing attitude control thrusters which have new construction and performance as well as the other similar thrusters.

Key words: Monopropellant rocket engine;Thermal control;Temperature field;Thermal analysis;Simulation model

王超,周旭东,汤建华,孙磊,华巍,杨建辉,杨玲琴. 单组元肼推力器温度场仿真及试验[J]. 推进技术, 2005, 26(1): 1-4.

单组元肼推力器温度场仿真及试验

Numerical and experimental studies for temperature field of monopropellant hydrazine thruster

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